#1. Air passes a normal shock wave. Which of the following statements is correct?
#2. The critical Mach number for an aerofoil equals the free stream airfoil Mach number at which:
#3. When the air has passed through a normal shock wave the Mach number is
#4. When the air is passing through a shock wave the static temperature will
#5. When the air is passing through a shock wave the density will
#6. When air has passed through a shock wave the speed of sound is
#7. Just above the critical Mach number the first evidence of a shock wave will appear at the
#8. Critical Mach-number is the :
#9. The loss of total pressure in a shock wave is due to the fact that
#10. Which of the following (1) aerofoils and (2) angles of attack will produce the lowest Mcrit values?
#11. In the transonic range the aeroplane characteristics are strongly determined by:
#12. Which of the following flight phenomena can happen at Mach Numbers below the critical Mach Number?
#13. The critical Mach Number of an aeroplane can be increased by:
#14. In transonic flight the ailerons will be less effective than in subsonic flight because:
#15. Two methods to increase the critical Mach Number are:
#16. If an aeroplane is flying at transonic speed with increasing Mach number the shock wave on the upper side of the wing
#17. To increase the critical Mach number a conventional aerofoil should
#18. The critical Mach number can be increased by
#19. Some aeroplanes have a ‘waist’ or ‘coke bottle’ contoured fuselage. This is done to
#20. The application of the area rule on aeroplane design will decrease the
#21. When comparing a rectangular wing and a swept back wing of the same wing area and wing loading, the swept back wing has the advantage of :
#22. What is the influence of decreasing aeroplane weight on Mcrit at constant IAS ?
#23. What is the effect of a decreasing aeroplane weight on Mcrit at n=1, when flying at constant IAS ? The value of Mcrit:
#24. How does stalling speed (IAS) vary with altitude?
#25. Which kind of flow separation occurs at the smallest angle of attack?
#26. At higher altitudes, the stall speed (IAS):
#27. Shock stall is:
#28. Which of the following flight phenomena can only happen at Mach Numbers above the critical Mach Number?
#29. Shock induced separation results in
#30. In the transonic range lift will decrease at the shock stall due to the
#31. The high speed buffet is induced by
#32. “”Tuck under”” is caused by (i) which movement of the centre of pressure of the wing and (ii) which change of the downwash angle at the location of the stabilizer.
#33. The consequences of exceeding Mcrit in a swept-wing aeroplane may be : (assume no corrective devices, straight and level flight)
#34. The Mach trim system will:
#35. The Mach trim system will prevent:
#36. When an aeroplane is flying through the transonic range with increasing Mach Number the centre of the pressure of the wing will move aft. This requires:
#37. Tuck under will happen
#38. The Mach-trim function is installed on most commercial jets in order to minimize the adverse effects of :
#39. What data may be obtained from the Buffet Onset Boundary chart?
#40. The maximum acceptable cruising altitude is limited by a minimum acceptable loadfactor because exceeding that altitude:
#41. Should a transport aeroplane fly at a higher Mach number than the ‘buffet-onset’ Mach number?
#42. A jet aeroplane is cruising at high altitude with a Mach-number, that provides a buffet margin of 0.3g incremental. In order to increase the buffet margin to 0.4g incremental the pilot must :
#43. The buffet margin :
#44. Vortex generators on the upper side of the wing surface will:
#45. Vortex generators on the upper side of the wing:
#46. Vortex generators mounted on the upper wing surface will
#47. How will the density and temperature change in a supersonic flow from a position in front of a shock wave to behind it ?
#48. At what speed does the front of a shock wave move across the earth’s surface?
#49. In supersonic flight, all disturbances produced by an aeroplane are:
#50. The bow wave will appear first at:
#51. If the Mach number of an aeroplane in supersonic flight is increased, the shock wave angles will
#52. When air has passed an expansion wave, the static pressure is:
#53. When the air is passing through an expansion wave the local speed of sound will
#54. When the air is passing through an expansion wave the Mach number will
#55. When the air is passing through an expansion wave the static temperature will
#56. In case of supersonic flow retarded by a normal shock wave a high efficiency (low loss in total pressure) can be obtained if the Mach number in front of the shock is
#57. Which statement is correct about an expansion wave in a supersonic flow ?1- The density in front of an expansion wave is higher than behind.2- The pressure in front of an expansion wave is higher than behind
#58. On a non swept wing, when the aerofoil is accelerated from subsonic to supersonic speeds, the aerodynamic centre :
#59. If an aeroplane is accelerated from subsonic to supersonic speeds, the centre of pressure will move:
#60. The aft movement of the centre of pressure during the acceleration through the transonic flight regime will:
#61. In supersonic flight aerofoil pressure distribution is:
#62. If a symmetrical aerofoil is accelerated from subsonic to supersonic speed the centre of lift will move
#63. The additional increase of drag at Mach Numbers above the critical Mach Number is due to:
#64. If the total sum of moments about one of its axis is not zero, an aeroplane:
#65. In which situation would the wing lift of an aeroplane in straight and level flight have the highest value ?
#66. If the sum of moments in flight is not zero, the aeroplane will rotate about:
#67. When an aeroplane with the centre of gravity forward of the centre of pressure of the combined wing / fuselage is in straight and level flight, the vertical load on the tailplane will be:
#68. An aeroplane, with a C.G. location behind the centre of pressure of the wing can only maintain a straight and level flight when the horizontal tail loading is:
#69. In a twin-engined jet powered aeroplane (engines mounted below the low wings) the thrust is suddenly increased. Which elevator deflection will be required to maintain the pitching moment zero ?
#70. Which of the following statements is correct?
#71. Positive static stability of an aeroplane means that once it has been displaced the :
#72. After a disturbance about the lateral axis, an aeroplane oscillates about the lateral axis at a constant amplitude. The aeroplane is:
#73. Which one of the following statements about the dynamic stability of a conventional aeroplane about the lateral axis is correct?
#74. The “”short period mode”” is an:
#75. An aeroplane that has positive static stability:
#76. A statically unstable aeroplane is:
#77. One of the requirements for dynamic stability is:
#78. The manoeuvrability of an aeroplane is best when the:
#79. Longitudinal static stability is created by the fact that the:
#80. The aerodynamic centre of the wing is the point, where:
#81. For a normal stable aeroplane, the centre of gravity is located:
#82. The max aft position of the centre of gravity is amongst others limited by the:
#83. A C.G location beyond the aft limit leads to:
#84. In what way is the longitudinal stability affected by the degree of positive camber of the aerofoil?
#85. Which part of an aeroplane provides the greatest positive contribution to the static longitudinal stability ?
#86. During landing of a low-winged jet aeroplane, the maximum elevator up deflection is normally required when the flaps are:
#87. The C.G. position of an aeroplane is forward of the neutral point in a fixed location. Speed changes cause a departure from the trimmed position. Which of the following statements about the stick force stability is correct?
#88. “”Tuck under”” is:
#89. “”Tuck under”” may happen at:
#90. Which of the following statements about a Mach trimmer is correct?
#91. In case the Mach trimmer fails:
#92. A Machtrimmer:
#93. The (1) stick force stability and the (2) manoeuvre stability are positively affected by:
#94. Which statement about stick force per g is correct?
#95. The value of the manoeuvre stability of an aeroplane is 150 N/g. The load factor in straight and level flight is 1. The increase of stick force necessary to achieve the load factor of 2.5 is:
#96. An aeroplane has static directional stability, in a side-slip to the right, initially the:
#97. The effect of a positive wing sweep on static directional stability is as follows:
#98. The effect of a high wing with zero dihedral is as follows:
#99. Which of the following lists aeroplane features that each increase static lateral stability ?
#100. Which type of wing arrangement decreases the static lateral stability of an aeroplane?
